Aerodynamic Control of the Pitch Attitude of the Tilt Rotor in Hovering

A new kind of rotated wing aircraft in hover pitch control mode was presented to ensure the stability of aircraft through its outer end of the rotary wing and aileron linkage. It is necessary to tilt the outer end of the wing and aileron to meet not only the aerodynamic characteristics of level flight but also the pneumatic and torque requirements when hovering,and meet the deflection angle of aileron which was installed in its outer end of the rotary wing to the hover pitch control requirements.Firstly,the NACA23012 airfoil is used to build the geometric model in CATIA and the unstructured mesh is generated in ICEM,then aerodynamic characteristics of the rotary wing and aileron when hovering was calculated by using Fluent,and analyzed the requirement of torque in hover,then,based on the calculation results,further modified airfoils satisfy the design requirements of the scheme.